BOUNDARY-LAYER DEVELOPMENT IN AXIAL COMPRESSORS AND TURBINES .4. COMPUTATIONS AND ANALYSES

This is Part Four of a four-part paper. It begins with Section 16.0 an d concludes the description of the comprehensive experiments and compu tational analyses that have led to a detailed picture of boundary laye r development on airfoil surfaces in multistage turbomachinery. In thi s part, the computational predictions made using several modem boundar y layer cones are presented. Both steady codes and an unsteady code we re evaluated. The results are compared with time-averaged and unsteady integral parameters measured for the boundary layers. Assessments are made to provide guidance in using the predictive codes to locate tran sition and predict loss. Conclusions from the computational analyses a re then presented.